Gas turbine combustor

ABSTRACT

A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a continuation of U.S. application Ser. No.13/539,559 filed on Jul. 2, 2012, which is based on and claims thebenefit of priority from Japanese Patent Application No. 2011-151310filed on Jul. 7, 2011, which are incorporated herein by reference intheir entirety.

FIELD OF THE INVENTION

A present disclosure relates to a gas turbine combustor for combustingfuel to produce combustion gas.

BACKGROUND

Conventionally, in order to control a combustion oscillation, the gasturbine combustor having a resonance device is known. The resonancedevice is called an acoustic liner and is attached to an outer peripheryof a combustor basket of the combustor.

For example, disclosed in Patent Literature 1 is a gas turbine combustorin which an acoustic liner having a hollow space (a resonance space) ismounted on an outer periphery of a cylindrical part of the combustor andthe hollow space communicates with acoustic absorption holes (acousticholes) formed in the cylindrical part of the combustor.

Moreover, arranging the acoustic absorption holes and the acoustic linernear a combustion area (i.e. near a flame) is also indicated, from aviewpoint of effectively controlling combustion oscillation (seeparagraph 0011).

On the other hand, the gas turbine combustor having a plurality ofresonance devices is known.

For example, a gas turbine combustor equipped with two acoustic linersin the direction of a flow of the combustion gas of a combustion lineris indicated by Patent Literature 2 and Patent Literature 3 (see FIG. 1of Patent Literature 2 and FIG. 2 of Patent Literature 3).

Moreover, disclosed in Patent Literature 4 is a gas turbine combustorhaving an acoustic liner and an acoustic damper connected to theacoustic liner mounted on the combustion liner (see FIG. 6).

Furthermore, disclosed in Patent Literature 5 is a gas turbine combustorhaving a plurality of damping devices attached to a transition piece.The damping device is formed of an acoustic liner and an acoustic damperconnected to the acoustic liner (see FIG. 17).

CITATION LIST Patent Literature

-   [PTL1]-   JP 2002-174427 A-   [PTL2]-   JP2006-97981 A-   [PTL3]-   JP 2008-20095 A-   [PTL4]-   JP 2007-132640 A-   [PTL5]-   JP 2006-266671 A

SUMMARY Technical Problem

It was conventionally though that, when the combustor basket isinstalled with one acoustic liner capable of suppressing the combustionoscillation of a broad frequency range (for example, about 1.5-5 kHz),problems, such as generation of cracks resulting from a combustionoscillation, were fully solvable.

However, as a result of diligent examination by the inventors, it wasconfirmed that the combustion oscillation of the particular highfrequency (for example, about 5.5 kHz) outside the frequency band of theabove-mentioned acoustic liner may also be generated depending onoperating conditions of a gas turbine.

This is considered due to the fact that, since the operating conditions(magnitude of a load) of the gas turbine is not always consistent, thelength of a flame formed in the inner space of the combustor basketfluctuates, and characteristics of combustion oscillation changedepending on the flame length.

And it became clear by further examination by these inventors, that thecombustion oscillation of the above particular high frequency takesplace when the flame position is shifted toward a downstream side in thedirection of the combustion gas flow compared to a positioncorresponding to the frequency band which can be suppressed by theacoustic liner, and also the combustion takes place near a wall surfaceof the combustor basket.

Then, it is conceivable, in reference to the disclosure of PatentLiterature 1, to make an acoustic liner broad compared with the formeracoustic liner and to expand the installation area of the acoustic linerto the flame position corresponding to the combustion oscillation of theabove-mentioned particular high frequency so as to arrange the acousticliner near the combustion zone (flame).

However, if the acoustic liner is increased in width, the number ofpurging holes formed in a housing of the acoustic liner will increase,the inflow of the compressed air into the housing through the purgingholes will increase, and the amount of the compressed air used forcombustion will decrease.

In contrast, although attaching two resonance devices is indicated byPatent Literature 2 through Patent Literature 5, there is no disclosureas to by what positional relation each resonance device is arranged toeffectively suppress the combustion oscillation at the above particularhigh frequency.

In view of the above-mentioned situation, it is an object of at leastone embodiment of the present invention to provide a gas turbinecombustor capable of reducing the combustion oscillation of highfrequency while inhibiting decline of the supply amount of thecompressed air for combustion.

According to at least one embodiment of the present invention, a gasturbine combustor comprises a combustor basket, a first resonancedevice, and a second resonance device. In the combustor basketcombustion gas flows and the combustion gas is produced by combustion offuel injected from at least one nozzle. The first resonance device ismounted on an outer surface of the combustor basket. The secondresonance device is for damping combustion oscillation of a frequencyhigher than the first resonance device and the second resonance deviceis mounted on the outer surface of the combustor basket so as to bedisposed on a downstream side from the first resonance device in a flowof the combustion gas. The first resonance device and the secondresonance device are acoustic liners each having a housing mounted tothe outer surface of the combustor basket. A resonance space surroundedby the housing and the outer surface of the combustor basketcommunicates with an interior space of the combustor basket via aplurality of acoustic holes formed in the combustor basket.

In the above gas turbine combustor, in addition to the first resonancedevice, the second resonance device is provided to damp the combustionoscillation of the frequency wave higher than the first resonancedevice. Thus, the combustion oscillation of a particular high-frequencywave below or above the frequency band of the first resonance device canbe damped by the second resonance device. Moreover, by arranging thesecond resonance device downstream from the first resonance device in aflow direction of the combustion gas, the second resonance device isarranged nearer to a flame position in the case of the combustionoscillation of the particular high-frequency wave occurring below orabove the frequency band of the first resonance device, therebyimproving the damping effect on the combustion oscillation of thehigh-frequency wave by the second resonance device. Further, by usingthe first and second resonance devices, instead of one wide resonancedevice, it is possible to suppress the increase of the mounting area ofthe resonance devices, and also to avoid the decline in the supplyamount of the compressed air for combustion by minimizing the number ofpurging holes which the resonance device normally has.

In some embodiments, the resonance space of the second resonance devicehas a height smaller than the resonance space of the first resonancedevice.

By setting the height of the resonance space of the second resonancedevice relatively small, the combustion oscillation of thehigh-frequency wave can be damped effectively by the second resonancedevice. Further, with the second resonance device being more compact,layout of the second resonance device is made easier.

The above gas turbine combustor may further comprise a transition piecefor introducing the combustion gas produced in the combustor basket to aturbine, a spring clip for connecting the upstream end of the transitionpiece and the downstream end of the combustor basket to each other byelastic force, and a baggy clip for pressing the spring clip toward theupstream end of the transition piece. The transition piece is arrangedso that an upstream end of the transition piece overlaps an outerperiphery of a downstream end of the combustor basket. The secondresonance device may be housed in a space surrounded by the baggy clipand the outer surface of the downstream end of the combustor basket.

By housing the second resonance device in the space surrounded by thebaggy clip and the outer surface of the downstream end of the combustorbasket, it is possible to utilize the space under the baggy clip.

In some embodiments, the at least one nozzle includes a pilot nozzlearranged on a center axis of the combustor basket and a plurality ofmain nozzles arranged on an outer circumference of the pilot nozzle, anda relationship of 0.8≤L₂/D₂≤1.1 is established where D₂ is a diameter ofthe combustor basket at a mounting position of the second resonancedevice and L₂ is a distance between a downstream end of a main-nozzleexternal cylinder surrounding the main nozzle and the mounting positionof the second resonance device.

As a result, the combustion oscillation of the particular high-frequencywave below or above the frequency band of the first resonance device canbe effectively suppressed by the second resonance device.

In some embodiments, a relationship of 0.05≤W₂/D₂≤0.3 is establishedwhere D₂ is a diameter of the combustor basket at a mounting position ofthe second resonance device and W₂ is a width of the resonance space ofthe second resonance device in a longitudinal direction of the combustorbasket.

As a result, while downsizing the second resonance device, the secondresonance device is capable of effectively suppressing the combustionoscillation of a particular high-frequency wave outside the frequencyband of the first resonance device.

In some embodiments, a relationship of 0.005≤h₂/D₂≤0.02 is establishedwhere D₂ is a diameter of the combustor basket at a mounting position ofthe second resonance device and h₂ is a height of the resonance space ofthe second resonance device.

As a result, while making the second resonance device compact, it ispossible to achieve a significant damping effect by the second resonancedevice damping the combustion oscillation of the high-frequency waveabove the frequency band of the first resonance device.

Solution to Problem

According to at least one embodiment of the present invention, inaddition to the first resonance device, the second resonance device isprovided to damp the combustion oscillation of the frequency wave higherthan the first resonance device. Thus, the combustion oscillation of aparticular high-frequency wave below or above the frequency band of thefirst resonance device can be damped by the second resonance device.Moreover, by arranging the second resonance device downstream from thefirst resonance device in a flow direction of the combustion gas, thesecond resonance device is arranged nearer to a flame position in thecase of the combustion oscillation of the particular high-frequency waveoccurring below or above the frequency band of the first resonancedevice, thereby improving the damping effect on the combustionoscillation of the high-frequency wave by the second resonance device.Further, by using the first and second resonance devices, instead of onewide resonance device, it is possible to suppress the increase of themounting area of the resonance devices, and also to avoid the decline inthe supply amount of the compressed air for combustion by minimizing thenumber of purging holes which the resonance device normally has.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 is a cross-sectional view of a gas turbine combustor in relationto an embodiment.

FIG. 2 is a cross-sectional view of the gas turbine combustor nearresonance devices in relation to an embodiment.

DETAILED DESCRIPTION

Embodiments of the present invention will now be described in detailwith reference to the accompanying drawings. It is intended, however,that unless particularly specified in these embodiments, dimensions,materials, shape, its relative positions and the like shall beinterpreted as illustrative only and not limitative of the scope of thepresent invention.

FIG. 1 is a cross-sectional view of the gas turbine combustor inrelation to an embodiment. FIG. 2 is a cross-sectional view of the gasturbine combustor near resonance devices in relation to an embodiment.

As shown in FIG. 1, a gas turbine combustor (hereinafter, simplydescribed as a “combustor”) 1 is provided with nozzles 2, 3 forinjecting fuel, a combustor basket (a combustor liner) 4 in which thecombustion gas produced by combustion of the fuel flows, and atransition piece 6 connected to the combustor basket 4.

The combustor 1 forms a gas turbine, with a compressor and a turbine. Inthe gas turbine, compressed air produced in the compressor is suppliedto the combustor 1 as combustion air and combustion gas produced in thecombustor 1 is supplied from the combustor basket 4 to the turbine viathe transition piece 6. In this manner, the turbine is driven by thecombustion gas.

The combustor 1 is a premix combustor of a multi-nozzle type with acombination of a pilot nozzle 2 and a main nozzle 3. The pilot nozzle 2is arranged on a center axis of the combustor basket 4. On an outercircumference of the pilot nozzle 2, a plurality of main nozzles 3 isarranged to surround the pilot nozzle 2. Tips of the main nozzles 3 arecovered by a main-nozzle external cylinder 5.

The fuel injected from the pilot nozzle 2 is ignited when mixed with thecompressed air, thereby forming a flame downstream from the pilot nozzle2. The fuel injected from the main nozzle 3 is ignited by the flameformed downstream from the pilot nozzle 2, thereby forming a flamedownstream from each of the main nozzles 3. As a result, a flow of thecombustion gas having a high temperature and flowing toward thetransition piece 6 is formed in an interior space of the combustorbasket 4.

The transition piece 6 is connected to the combustor basket 4 by meansof a spring clip 8. The transition piece 6 is arranged on an outercircumferential side of the combustor basket 4 and an upstream end ofthe transition piece 6 overlaps a downstream end of the combustor basket4. The spring clip 8 has one end fixed to the outer periphery of thedownstream end of the combustor basket 4 and the other end being a freeend. Thus, the combustor basket 4 and the transition piece 6 areconnected to each other by an elastic force of the spring clip 8.Further, a baggy clip 9 is provided between the spring clip 8 and thecombustor basket 4. The baggy clip 9 presses the spring clip 8 againstthe inner periphery of the transition piece 6. In this manner, thecombustor basket 4 and the transition piece 6 are firmly connected toeach other.

On the outer surface of the combustor basket 4, a first resonance device10 and a second resonance device 20 are provided to reduce combustionoscillation. The first resonance device 10 and the second resonancedevice 20 may be arranged over the entire circumference of the combustorbasket 4, or partially arranged in the circumferential direction of thecombustor basket 4.

As shown in FIG. 2, the first resonance device 10 is an acoustic linerwith a first housing 12 attached to the outer surface of the combustorbasket 4 by welding. A first resonance space 14 is surrounded by thefirst housing 12 and the outer surface of the combustor basket 4. Thefirst resonance space 14 communicates with the interior space of thecombustor basket 4 via a plurality of acoustic holes 16 formed in thecombustor basket 4. Thus, air oscillation (a pressure wave) caused bythe combustion oscillation generated in the combustor basket 4 is caughtin the acoustic holes 16 so as to resonate. More specifically, the airin the first resonance space 14 and the air in the acoustic holes 16together form a resonant system as the air in the first resonance space14 functions as a spring. With respect to oscillation of a resonantfrequency of this resonant system, the air in the acoustic hole 16resonates intensely. The friction generated in the process decreasesamplitude of the combustion oscillation.

Further, a frequency band of the combustion oscillation that can bedamped by the first resonance device 10 is arbitrarily settable byadjusting the diameter of the acoustic hole 16 (the sectional area), thesize of the first resonance space 14 (a height h₁ and a width W₁ of thefirst resonance space 14), and the like.

Further, in the first housing 12, a purging hole 18 is formed so that apart of the compressed air (the combustion air) flowing outside thecombustor basket 4 enters the first resonance space 14. This preventsdamages of the first housing 12 caused by contacting the hightemperature combustion gas. The compressed air flows in a directionopposite to the combustion gas flowing in the interior space of thecombustor basket 4, as shown in FIG. 2.

In some embodiments, a mounting position of the first resonance device10 is determined so that a relationship of 0.4≤L₁/D₁≤0.7 is establishedwhere D₁ is a diameter (an inner diameter) of the combustor basket 4 atthe mounting position of the first resonance device 10 (see FIG. 1) andL₁ is a distance between a downstream end of the main-nozzle externalcylinder 5 and the mounting position of the first resonance device 10(see FIG. 2). The mounting position of the first resonance device 10,herein, is a center position of a width of the first resonance device 10in a longitudinal direction of the combustor basket 4.

Further, in some embodiments, a width W₁ of the first resonance space 14in the longitudinal direction of the combustor basket 4 (see FIG. 2) isdetermined so that a relationship of 0.3≤W₁/D₁≤0.6 is established whereD₁ is the diameter of the combustor basket 4 at the mounting position ofthe first resonance device 10.

Furthermore, in some embodiments, a height h₁ of the first resonancespace 14 (see FIG. 2) is determined so that a relationship of0.03≤h₁/D₁≤0.1 is established where D₁ is the diameter of the combustorbasket 4 at the mounting position of the first resonance device 10.

In contrast, the second resonance device 20 is arranged on a downstreamside from the first resonance device 10 in a flow of the combustion gas.For instance, the second resonance device 20 may be arranged in the areawhere the transition piece 6 overlaps the combustor basket 4.

In at least one embodiment, a mounting position of the second resonancedevice 20 is determined so that a relationship of 0.8≤L₂/D₂≤1.1 isestablished where D₂ is a diameter (an inner diameter) of the combustorbasket 4 at the mounting position of the second resonance device 20 (seeFIG. 1) and L₂ is a distance between the downstream end of themain-nozzle external cylinder 5 and the mounting position of the secondresonance device 20 (see FIG. 2). As a result, the second resonancedevice 20 is arranged closer to the flame position when the combustionoscillation of high frequency occurs and thus, the combustionoscillation of high frequency can be effectively suppressed by thesecond resonance device 20.

The mounting position of the second resonance device 20, herein, is acenter position of a width of the second resonance device 20 in alongitudinal direction of the combustor basket 4.

Just like the first resonance device 10, the second resonance device 20is also an acoustic liner having a second housing 22 attached to theouter surface of the combustor basket 4. A second resonance space 24 issurrounded by the second housing 22 and the outer surface of thecombustor basket 4. The second resonance space 24 communicates with theinterior space of the combustor basket 4 via a plurality of acousticholes 26 formed in the combustor basket 4. Thus, with a mechanismsimilar to the case of the first resonance device 10, the resonancedevice 20 is capable of damping the combustion oscillation of aprescribed frequency. In the second housing 22, a purging hole 28 isformed so that a part of the compressed air flowing outside thecombustor basket 4 enters the second resonance space 24.

A frequency band of the combustion oscillation that can be damped by thesecond resonance device 20 is arbitrarily settable by adjusting thediameter (the sectional area) of the acoustic hole 26, the size of thesecond resonance space 24 (a height h₂ and a width W₂ of the secondresonance space 24), and the like. Further, the frequency band of thecombustion oscillation that can be damped by the second resonance device20 is set higher than the frequency band of the combustion oscillationthat can be damped by the first resonance device 10.

In at least one embodiment, a width W₂ of the second resonance space 24in the longitudinal direction of the combustor basket 4 (see FIG. 2) isdetermined so that a relationship of 0.05≤W₂/D₂≤0.3 is established whereD₂ is a diameter of the combustor basket 4 at the mounting position ofthe second resonance device 20.

As a result, while downsizing the second resonance device 20, the secondresonance device 20 is capable of effectively suppressing the combustionoscillation of a particular high-frequency wave outside the frequencyband of the first resonance device 10.

Further, in at least one embodiment, a height h₂ of the second resonancespace 24 (see FIG. 2) is determined so that a relationship of0.005≤h₂/D₂≤0.02 is established where D₂ is the diameter of thecombustor basket 4 at the mounting position of the second resonancedevice 20.

As a result, while downsizing the second resonance device 20, it ispossible to achieve a significant damping effect on the combustionoscillation of the high-frequency wave by the second resonance device20.

Further, in at least one embodiment, the height h₂ of the secondresonance space 24 is smaller than the height h₁ of the first resonancespace 14.

By setting the height h₂ of the second resonance space 24 of the secondresonance device 20 relatively small in this manner, the combustionoscillation of the high-frequency wave can be damped effectively in thesecond resonance device 20. Further, by downsizing the second resonancedevice 20, layout of the second resonance device 20 is made easier. Forinstance, it becomes possible to house the second resonance device 20 ina space surrounded by the baggy clip 9 and the outer surface of thecombustor basket 4, thereby utilizing the space under the baggy clip 9.

As described above, in the above embodiments, in addition to the firstresonance device 10, the second resonance device 20 is provided to dampthe combustion oscillation of the frequency wave higher than the firstresonance device 10. Thus, the combustion oscillation of the particularhigh-frequency wave below or above the frequency band of the firstresonance device 10 can be damped by the second resonance device 20.Moreover, by arranging the second resonance device 20 downstream fromthe first resonance device 10 in the flow of the combustion gas, thesecond resonance device 20 is arranged nearer to the flame position ofthe case when the combustion oscillation of the particularhigh-frequency wave occurs below or above the frequency band of thefirst resonance device 10, thereby improving the damping effect on thecombustion oscillation of the high-frequency wave by the secondresonance device 20. Further, by arranging the first and secondresonance devices 10, 20, instead of one wide resonance device, it ispossible to suppress the increase of the mounting area of the resonancedevices 10, 20, and also to avoid the decline in the supply amount ofthe compressed air for combustion by minimizing the number of thepurging holes 18, 28 which the resonance device normally has.

While the embodiments of the present invention have been described, itis obvious to those skilled in the art that various changes may be madewithout departing from the scope of the invention.

REFERENCE SIGNS LIST

-   1 Gas turbine combustor (Combustor)-   2 Pilot nozzle-   3 Main nozzle-   4 Combustor basket-   5 Main-nozzle external cylinder-   6 Transition piece-   8 Spring clip-   9 Baggy clip-   10 First resonance device-   12 First housing-   14 First resonance space-   16 Acoustic hole-   18 Purging hole-   20 Second resonance device-   22 Second housing-   24 Second resonance space-   26 Acoustic hole-   28 Purging hole

The invention claimed is:
 1. A gas turbine combustor comprising: acombustor basket in which combustion gas flows, the combustion gas beingproduced by combustion of fuel injected from at least one nozzle; afirst resonance device mounted on an outer surface of the combustorbasket; and a second resonance device for damping combustion oscillationof a frequency higher than the first resonance device, the secondresonance device being mounted on the outer surface of the combustorbasket so as to be disposed on a downstream side from the firstresonance device in a flow of the combustion gas, wherein the firstresonance device is a first acoustic liner having a first housingmounted to the outer surface of the combustor basket, the first housingforming a first resonance space, wherein the second resonance device isa second acoustic liner having a second housing mounted to the outersurface of the combustor basket, the second housing forming a secondresonance space, wherein the first resonance space and the secondresonance space each communicate with an interior space of the combustorbasket via a plurality of acoustic holes formed in the combustor basket,and wherein the second resonance device is housed in a first spacesurrounded by an outer surface of a downstream end of the combustorbasket and an upstream end of a transition piece for introducing thecombustion gas produced in the combustor basket to a turbine, thetransition piece being arranged so that the upstream end of thetransition piece overlaps an outer periphery of the downstream end ofthe combustor basket, wherein the second resonance space is directlycommunicated with the interior space of the combustor basket via theplurality of acoustic holes not through the first resonance space.
 2. Agas turbine combustor, comprising: a combustor basket in whichcombustion gas flows, the combustion gas being produced by combustion offuel injected from at least one nozzle; a first resonance device mountedon an outer surface of the combustor basket; and a second resonancedevice mounted on the outer surface of the combustor basket so as to bedisposed on a downstream side from the first resonance device in a flowof the combustion gas, wherein the first resonance device and the secondresonance device each have a respective resonance space, wherein eachresonance space is surrounded by the outer surface of the combustorbasket and a respective acoustic liner mounted to the outer surface ofthe combustor basket, wherein each resonance space communicates with aninterior space of the combustor basket via a respective plurality ofacoustic holes formed in the combustor basket, and wherein the secondresonance device is housed in a first space surrounded by an outersurface of a downstream end of the combustor basket and an upstream endof a transition piece for introducing the combustion gas produced in thecombustor basket to a turbine, the transition piece being arranged sothat the upstream end of the transition piece overlaps an outerperiphery of the downstream end of the combustor basket, wherein the gasturbine combustor further comprises a clip for connecting the upstreamend of the transition piece to the downstream end of the combustorbasket to each other, the clip being disposed in a space surrounded bythe upstream end of the transition piece and the outer surface of thedownstream end of the combustor basket, wherein the second resonancedevice is housed in a second space surrounded by the clip and the outersurface of the downstream end of the combustor basket.
 3. The gasturbine combustor according to claim 1, further comprising a baggy clipfor connecting the upstream end of the transition piece to thedownstream end of the combustor basket to each other, the baggy clipbeing disposed in the first space, wherein the second resonance deviceis housed in a second space surrounded by the baggy clip and the outersurface of the downstream end of the combustor basket.
 4. The gasturbine combustor according to claim 1, further comprising: a springclip for connecting the upstream end of the transition piece to thedownstream end of the combustor basket to each other, the spring clipbeing disposed in the first space; and a baggy clip for pressing thespring clip toward the upstream end of the transition piece, wherein thesecond resonance device is housed in a second space surrounded by thebaggy clip and the outer surface of the downstream end of the combustorbasket.
 5. The gas turbine combustor according to claim 1, wherein theresonance space of the second resonance device has a first heightsmaller than a second height of the resonance space of the firstresonance device.
 6. The gas turbine combustor according to claim 1,wherein the nozzle includes a pilot nozzle arranged on a center axis ofthe combustor basket and a plurality of main nozzles arranged on anouter circumference of the pilot nozzle, and wherein a relationship of0.8≤L2/D2≤1.1 is established where D2 is a diameter of the combustorbasket at a mounting position of the second resonance device and L2 is adistance between a downstream end of a main-nozzle external cylindersurrounding the main nozzle and the mounting position of the secondresonance device.
 7. The gas turbine combustor according to claim 1,wherein a relationship of 0.05≤W2/D2≤0.3 is established where D2 is adiameter of the combustor basket at a mounting position of the secondresonance device and W2 is a width of the resonance space of the secondresonance device in a longitudinal direction of the combustor basket. 8.The gas turbine combustor according to claim 1, wherein a relationshipof 0.005≤h2/D2≤0.02 is established where D2 is a diameter of thecombustor basket at a mounting position of the second resonance deviceand h2 is a height of the resonance space of the second resonancedevice.